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Non-axisymmetric airfoil platform shaping

a technology of airfoil platform and axis, which is applied in the direction of machines/engines, stators, liquid fuel engines, etc., can solve the problems of reducing the overall reducing the efficiency of the turbine, and losing the hot combustion gases into

Active Publication Date: 2015-05-26
GE INFRASTRUCTURE TECH INT LLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The invention is a new design for a blade and nozzle assembly for a turbine. The blade assembly includes a mounting portion, base, and blade, while the nozzle assembly includes a mounting portion, nozzle blade, and nozzle base. These designs have a curved portion on the leading or trailing edge, which improves performance and efficiency of the turbine. This results in better performance and reliability of the turbine.

Problems solved by technology

This essentially represents a loss of the hot combustion gases into the wheel space, which reduces the overall efficiency of the turbine.
Nevertheless, there is still a problem with loss of the hot combustion gases, which represents an undesirable inefficiency of the turbine.

Method used

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  • Non-axisymmetric airfoil platform shaping
  • Non-axisymmetric airfoil platform shaping
  • Non-axisymmetric airfoil platform shaping

Examples

Experimental program
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Embodiment Construction

[0023]As explained above, angel wings had been added to turbine blade assemblies, as shown in FIG. 2, to help prevent the hot combustion gases from the hot gas flow path from penetrating down into the wheel space of a turbine. In the blade assembly illustrated in FIG. 2, two angel wings 32 and 33 are formed on the leading side of the blade assembly, and two angel wings 34 and 35 are formed on the rear side of the blade assembly. In addition, the base upon which the blade is mounted includes a leading edge 47 and a trailing edge 49. The blade 40 extends upward from the base 45 and also includes a leading edge 42 and a trailing edge 46. A cap 43 is formed on the top of the blade 40.

[0024]FIG. 3 is a part cross-sectional view taken along line in FIG. 1. The cross section cuts through three adjacent turbine blades which are attached to a rotating shaft of the turbine. The row of turbine blades is positioned between two adjacent rows of nozzles. In FIG. 3, the row of nozzles on the left ...

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Abstract

Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and / or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and / or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and / or trailing edges of nozzle assemblies of a turbine.

Description

BACKGROUND OF THE INVENTION[0001]The invention is related to turbines which include turbine blades connected to a rotating shaft of the turbine and nozzles which direct steam or combustion gases to the nozzles.[0002]In a typical turbine used in the power generation industry, fuel is burned in a combustion zone and the hot combustion gases are then directed to the turbine section. In the turbine section, as illustrated in FIG. 1, a plurality of blade assemblies are mounted on a rotating shaft 16. The blade assemblies are attached around the exterior circumference of the rotating shaft 16. Each row of blade assemblies is positioned between an adjacent pair of rows of nozzles or vanes 16, 20. As shown in FIG. 1, a first row of turbine blades 22 is positioned between an adjacent pair of nozzles 18 and 20.[0003]The first row of nozzles 18 directs the hot combustion gases in a desired direction as it impinges upon the turbine blades 22. The passage of the combustion gas over the turbine b...

Claims

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Application Information

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Patent Type & Authority Patents(United States)
IPC IPC(8): F01D5/14F01D11/02
CPCF01D5/141F01D5/143F01D11/02F01D5/142
Inventor KNEELAND, ANDREW RAYGARCIA-CRESPO, ANDRES JOSEBOYER, BRADLEY T.VANDEPUTTE, THOMAS WILLIAMPIERRE, SYLVAIN
Owner GE INFRASTRUCTURE TECH INT LLC